摘要
使用类别形状函数变换(CST)参数化方法对超声速翼身组合体的机身和机翼外形进行参数化表示,在充分利用机翼与机身之间气动干扰的基础上提出了基于远场组元的机翼和机身激波阻力协同优化(CoFCE)算法,并对其计算量和优化结果同机翼和机身外形交替进行优化的扩展的远场组元(EFCE)激波阻力优化方法开展对比。研究结果表明:随着参数数量的增加,CoFCE算法的计算量更大,其优化效果明显优于EFCE算法;经过CoFCE方法优化的翼身组合体超声速巡航状态下的升阻比有大幅提高。
in this paper the wing and fuselage shapes of a supersonic wing-body are represented by class-shape-transforma- tion (CST) parameterization, and a method of supersonic wing-body wave drag co-optimization based on far-field composite elements (CoFCE) is proposed by taking advantage of the aerodynamic interference of the wing and the fuselage shapes. Optimization effect and computation cost comparisons between the OoFCE method and the extended far-field composite ele- ment (EFQE) wave drag optimization method are carried out. The study demonstrates that as the parameter number increa- ses more computation costs are required and significantly better optimization results can be achieved by the CoFOE method than by the EFOE method. The OoFCE optimizes wing-body yields higher lift to drag ratios in supersonic cruise conditions.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2013年第11期2510-2519,共10页
Acta Aeronautica et Astronautica Sinica
关键词
参数化
超声速飞行器
激波
减阻
外形优化
parameterization
supersonic aircraft
shock wave
drag reduction
shape optimization